Retention ring with removal features for gas turbine engine

ABSTRACT

A retention ring for a gas turbine engine according to an example of the present disclosure includes, among other things, a main body extending in a circumferential direction about an axis to establish a continuous hoop having a first diameter and a second diameter. The main body includes first and second circumferential faces along opposite sides of the main body. The first circumferential face is dimensioned to abut a gas turbine engine component. The main body includes at least one removal feature dimensioned to sever in response to engagement with a cutting tool. A method of assembly is also disclosed.

STATEMENT REGARDING FEDERALLY SPONSORED RESEARCH OR DEVELOPMENT

This invention was made with government support awarded by the UnitedStates. The Government has certain rights in this invention.

BACKGROUND

This disclosure relates to retention of gas turbine engine components.

A gas turbine engine typically includes at least a compressor section, acombustor section and a turbine section. The compressor sectionpressurizes air into the combustion section where the air is mixed withfuel and ignited to generate an exhaust gas flow. The exhaust gas flowexpands through the turbine section to drive the compressor section and,if the engine is designed for propulsion, a fan section.

One or more components can be releasably secured in the engine, such asa seal that establishes a sealing relationship with an adjacentcomponent such as a rotatable shaft. The seal may be secured to ahousing with a split ring.

SUMMARY

A retention ring for a gas turbine engine according to an example of thepresent disclosure includes a main body extending in a circumferentialdirection about an axis to establish a continuous hoop having a firstdiameter and a second diameter. The main body includes first and secondcircumferential faces along opposite sides of the main body that extendin a radial direction between the first and second diameters. The firstcircumferential face is dimensioned to abut a gas turbine enginecomponent. The main body includes at least one removal featuredimensioned to sever in response to engagement with a cutting tool. Theremoval feature includes a notch and a first groove. The notch extendsin an axial direction along a face of the second diameter between thefirst and second circumferential faces. The first groove extends in theradial direction from a floor of the notch along the firstcircumferential face to a face of the first diameter.

In a further embodiment of any of the foregoing embodiments, the atleast one removal feature includes a plurality of removal featuresdistributed about the axis.

In a further embodiment of any of the foregoing embodiments, the firstdiameter is an inner diameter of the continuous hoop, and the seconddiameter is an outer diameter of the continuous hoop.

In a further embodiment of any of the foregoing embodiments, the atleast one removal feature includes a second groove extending in theradial direction from the floor of the notch along the secondcircumferential face to the face of the second diameter.

In a further embodiment of any of the foregoing embodiments, the firstgroove is aligned with the second groove relative to the circumferentialdirection.

In a further embodiment of any of the foregoing embodiments, a firstwidth of the first groove at the floor of the notch is less than amaximum width of the notch, the first width and the maximum widthrelative to the circumferential direction. A first length of the firstgroove is greater than a maximum height of the notch, the first lengthand the maximum height relative to the radial direction.

In a further embodiment of any of the foregoing embodiments, the mainbody comprises a metallic material.

A gas turbine engine according to an example of the present disclosureincludes a support extending about an engine longitudinal axis. Thesupport includes a shoulder and a retention slot. The gas turbine engineincludes a gas turbine engine component and a retention ring received inthe retention slot. The retention ring includes a main body having afirst diameter and a second diameter. The main body includes first andsecond circumferential faces along opposite sides of the main body. Thefirst circumferential face is dimensioned to abut the gas turbine enginecomponent. The main body includes at least one removal feature. The atleast one removal feature includes a notch and a first groove. The notchextends inwardly from a face of the second diameter that is received inthe retention slot. The first groove extends radially from a floor ofthe notch along the first circumferential face. The floor of the notchis radially offset from the retention slot relative to the enginelongitudinal axis to establish a clearance gap. The clearance gap isdimensioned to receive a cutting tool movable along the first groove tosever the retention ring.

In a further embodiment of any of the foregoing embodiments, the mainbody extends circumferentially about the engine longitudinal axis toestablish a continuous hoop.

In a further embodiment of any of the foregoing embodiments, the firstdiameter is an inner diameter of the retention ring, the second diameteris an outer diameter of the retention ring, and the groove extends fromthe notch to the inner diameter of the retention ring.

In a further embodiment of any of the foregoing embodiments, theshoulder and the retention slot extend circumferentially about theengine longitudinal axis. The retention slot is radially outward of theshoulder. The gas turbine engine component extends radially inward ofthe first circumferential face of the main body.

In a further embodiment of any of the foregoing embodiments, the atleast one removal feature includes a plurality of removal featurescircumferentially distributed about an axis of the retention ring.

In a further embodiment of any of the foregoing embodiments, the gasturbine engine component is an annular seal dimensioned to engage arotatable component.

A method of assembly for a gas turbine engine according to an example ofthe present disclosure includes changing a temperature of at least oneof a retention ring and a support to meet a respective predeterminedtemperature threshold when the retention ring is in a first position toestablish an assembly clearance when the retention ring is in a secondposition relative to the support. The assembly clearance is establishedbetween a second diameter of the retention ring and a retention slot ofthe support. The retention ring includes a main body establishing acontinuous hoop including a first diameter and the second diameter. Themain body includes at least one removal feature having a notch and afirst groove. The notch extends along the second diameter of theretention ring. The first groove extends along a first circumferentialface of the main body to the first diameter of the retention ring. Themethod includes moving a gas turbine engine component along an assemblyaxis such that the gas turbine engine component is adjacent to ashoulder of the support, moving the retention ring along the assemblyaxis from the first position to the second position to establish theassembly clearance such that the retention ring is axially aligned with,but is spaced apart from, the retention slot, and reducing the assemblyclearance in response to the temperature no longer meeting therespective predetermined temperature threshold. The reducing step occurssuch that the second diameter of the retention ring is captured in theretention slot, such that the gas turbine engine component is trappedbetween the shoulder of the support and the first circumferential faceof the retention ring, and such that a clearance gap is establishedbetween the support and a floor of the notch.

In a further embodiment of any of the foregoing embodiments, the atleast one removal feature includes a plurality of removal featurescircumferentially distributed along the first circumferential face.

A further embodiment of any of the foregoing embodiments, the methodincludes severing the retention ring in response to moving a cuttingtool into the clearance gap and then along the first groove, andremoving at least one portion of the severed retention ring from theretention slot, and then removing the gas turbine engine component fromthe support.

In a further embodiment of any of the foregoing embodiments, a maximumheight of the notch is greater than a maximum height of the retentionslot at a common circumferential position relative to an enginelongitudinal axis.

In a further embodiment of any of the foregoing embodiments, the atleast one removal feature includes a second groove extending from thenotch. The notch interconnects the first and second grooves. The secondgroove extends along a second circumferential face of the retention bodysuch that the second groove is circumferentially aligned with the firstgroove. The severing step includes moving the cutting tool along acutting path intersecting both the first and second grooves to establisha pathway between the first and second grooves.

In a further embodiment of any of the foregoing embodiments, the seconddiameter of the retention ring is an outer diameter. The retention slotis established along a radially inward facing surface of the supportrelative to the assembly axis. The assembly clearance is establishedbetween the outer diameter of the retention ring and the radially inwardfacing surface of the support. The respective predetermined temperaturethreshold includes a first predetermined temperature thresholdassociated with the support and a second predetermined temperaturethreshold associated with the retention ring. The step of changing thetemperature includes heating the support above the first predeterminedtemperature threshold to cause the retention slot of the support toexpand relative to the assembly axis, and cooling the retention ringbelow the second predetermined threshold to cause the outer diameter ofthe retention ring to contract relative to the assembly axis, the secondpredetermined threshold being less than the first predeterminedthreshold.

In a further embodiment of any of the foregoing embodiments, the supportcomprises a first metallic material, and the main body comprises asecond metallic material.

The present disclosure may include any one or more of the individualfeatures disclosed above and/or below alone or in any combinationthereof.

The various features and advantages of this invention will becomeapparent to those skilled in the art from the following detaileddescription of an embodiment. The drawings that accompany the detaileddescription can be briefly described as follows.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 shows an example gas turbine engine.

FIG. 2 illustrates another example gas turbine engine.

FIG. 3 illustrates a perspective view of an exemplary assembly in a coldassembly state including a retention ring.

FIG. 4 illustrates an axial view of the retention ring in the assemblyof FIG. 3 .

FIG. 5 illustrates an isolated perspective view of a portion of theretention ring of FIG. 4 .

FIG. 6 illustrates a perspective view of the assembly of FIG. 3including engagement of the retention ring with a tool.

FIG. 7 illustrates a plan view of another exemplary retention ring.

FIG. 8 illustrates a method of assembly for a gas turbine engine.

FIG. 9 illustrates components of the assembly of FIG. 3 in anuninstalled state.

DETAILED DESCRIPTION

Referring to FIG. 1 , a gas turbine engine 10 includes a fan section 11,a compressor section 12, a combustor section 13, and a turbine section14. Air entering into the fan section 11 is initially compressed and fedto the compressor section 12. In the compressor section 12, the incomingair from the fan section 11 is further compressed and communicated tothe combustor section 13. In the combustor section 13, the compressedair is mixed with gas and ignited to generate a hot exhaust stream E.The hot exhaust stream E is expanded through the turbine section 14 todrive the fan section 11 and the compressor section 12. The exhaustgasses E flow from the turbine section 14 through an exhaust linerassembly 18.

FIG. 2 schematically illustrates a gas turbine engine 20 according toanother example. The gas turbine engine 20 is disclosed herein as atwo-spool turbofan that generally incorporates a fan section 22, acompressor section 24, a combustor section 26 and a turbine section 28.The fan section 22 drives air along a bypass flow path B in a bypassduct defined within a housing 15 such as a fan case or nacelle, and alsodrives air along a core flow path C for compression and communicationinto the combustor section 26 then expansion through the turbine section28. Although depicted as a two-spool turbofan gas turbine engine in thedisclosed non-limiting embodiment, it should be understood that theconcepts described herein are not limited to use with two-spoolturbofans as the teachings may be applied to other types of turbineengines including three-spool architectures.

The exemplary engine 20 generally includes a low speed spool 30 and ahigh speed spool 32 mounted for rotation about an engine centrallongitudinal axis A relative to an engine static structure 36 viaseveral bearing systems 38. It should be understood that various bearingsystems 38 at various locations may alternatively or additionally beprovided, and the location of bearing systems 38 may be varied asappropriate to the application.

The low speed spool 30 generally includes an inner shaft 40 thatinterconnects, a first (or low) pressure compressor 44 and a first (orlow) pressure turbine 46. The inner shaft 40 is connected to the fan 42through a speed change mechanism, which in exemplary gas turbine engine20 is illustrated as a geared architecture 48 to drive a fan 42 at alower speed than the low speed spool 30. The high speed spool 32includes an outer shaft 50 that interconnects a second (or high)pressure compressor 52 and a second (or high) pressure turbine 54. Acombustor 56 is arranged in the exemplary gas turbine 20 between thehigh pressure compressor 52 and the high pressure turbine 54. Amid-turbine frame 57 of the engine static structure 36 may be arrangedgenerally between the high pressure turbine 54 and the low pressureturbine 46. The mid-turbine frame 57 further supports bearing systems 38in the turbine section 28. The inner shaft 40 and the outer shaft 50 areconcentric and rotate via bearing systems 38 about the engine centrallongitudinal axis A which is collinear with their longitudinal axes.

The core airflow is compressed by the low pressure compressor 44 thenthe high pressure compressor 52, mixed and burned with fuel in thecombustor 56, then expanded through the high pressure turbine 54 and lowpressure turbine 46. The mid-turbine frame 57 includes airfoils 59 whichare in the core airflow path C. The turbines 46, 54 rotationally drivethe respective low speed spool 30 and high speed spool 32 in response tothe expansion. It will be appreciated that each of the positions of thefan section 22, compressor section 24, combustor section 26, turbinesection 28, and fan drive gear system 48 may be varied. For example,gear system 48 may be located aft of the low pressure compressor, or aftof the combustor section 26 or even aft of turbine section 28, and fan42 may be positioned forward or aft of the location of gear system 48.

The engine 20 in one example is a high-bypass geared aircraft engine. Ina further example, the engine 20 bypass ratio is greater than about six(6), with an example embodiment being greater than about ten (10), andcan be less than or equal to about 18.0, or more narrowly can be lessthan or equal to 16.0. The geared architecture 48 is an epicyclic geartrain, such as a planetary gear system or other gear system, with a gearreduction ratio of greater than about 2.3. The gear reduction ratio maybe less than or equal to 4.0. The low pressure turbine 46 has a pressureratio that is greater than about five. The low pressure turbine pressureratio can be less than or equal to 13.0, or more narrowly less than orequal to 12.0. In one disclosed embodiment, the engine 20 bypass ratiois greater than about ten (10:1), the fan diameter is significantlylarger than that of the low pressure compressor 44, and the low pressureturbine 46 has a pressure ratio that is greater than about five 5:1. Lowpressure turbine 46 pressure ratio is pressure measured prior to aninlet of low pressure turbine 46 as related to the pressure at theoutlet of the low pressure turbine 46 prior to an exhaust nozzle. Thegeared architecture 48 may be an epicycle gear train, such as aplanetary gear system or other gear system, with a gear reduction ratioof greater than about 2.3:1 and less than about 5:1. It should beunderstood, however, that the above parameters are only exemplary of oneembodiment of a geared architecture engine and that the presentinvention is applicable to other gas turbine engines including directdrive turbofans.

A significant amount of thrust is provided by the bypass flow B due tothe high bypass ratio. The fan section 22 of the engine 20 is designedfor a particular flight condition—typically cruise at about 0.8 Mach andabout 35,000 feet (10,668 meters). The flight condition of 0.8 Mach and35,000 ft (10,668 meters), with the engine at its best fuelconsumption—also known as “bucket cruise Thrust Specific FuelConsumption (‘TSFC’)”—is the industry standard parameter of lbm of fuelbeing burned divided by lbf of thrust the engine produces at thatminimum point. The engine parameters described above and those in thisparagraph are measured at this condition unless otherwise specified.“Low fan pressure ratio” is the pressure ratio across the fan bladealone, without a Fan Exit Guide Vane (“FEGV”) system. The low fanpressure ratio as disclosed herein according to one non-limitingembodiment is less than about 1.45, or more narrowly greater than orequal to 1.25. “Low corrected fan tip speed” is the actual fan tip speedin ft/sec divided by an industry standard temperature correction of[(Tram ° R)/(518.7° R)]^(0.5). The “Low corrected fan tip speed” asdisclosed herein according to one non-limiting embodiment is less thanabout 1150.0 ft/second (350.5 meters/second), and can be greater than orequal to 1000.0 ft/second (304.8 meters/second).

FIG. 3 illustrates an exemplary assembly 60 for a gas turbine engine.The assembly 60 can include one or more retention features for securingand removing gas turbine engine component(s) in a gas turbine engine,such as the gas turbine engine 10 of FIG. 1 or the gas turbine engine 20of FIG. 2 . Although the assembly 60 is primarily discussed in relationto a gas turbine engine including a fan, other systems can benefit fromthe teachings disclosed herein including a gas turbine engine lacking afan for propulsion.

The assembly 60 can include a first gas turbine engine component 62, asecond gas turbine engine component 64 and a retention ring 66. Theretention ring 66 can be arranged to secure the first and secondcomponents 62, 64 to the each other. The first and second components 62,64 and retention ring 66 can be static or rotatable components. Thefirst component 62 can be a support (e.g., static support piece) such asa housing or another portion of a static structure, such as the enginestatic structure 36 (FIG. 2 ). The second component 64 (e.g., retainedengine hardware) can be an annular seal dimensioned to engage a thirdgas turbine engine component 68 in a cold assembly state (shown indashed lines for illustrative purposes). The third component 68 can be arotatable component such as a rotatable shaft, including one of theshafts 40, 50 (FIG. 2 ). The second and third components 64, 68 cancooperate to establish a sealing relationship.

The first and second components 62, 64 and retention ring 66 can extendalong an assembly axis AA. The first and second components 62, 64 and/orretention ring 66 can have a generally annular geometry and can extendin a circumferential direction T about the assembly axis AA. Theassembly axis AA can be substantially collinear or otherwise parallelwith the engine longitudinal axis A of the engines 10, 20. For thepurposes of this disclosure, the terms “substantially,” “about” and“approximately” mean±5 percent of the stated value or relationshipunless otherwise indicated.

The first component 62 can include a main body 70 including a shoulder70S and a retention slot 70R. The shoulder 70S and retention slot 70Rcan be spaced apart in an axial direction X relative to the assemblyaxis AA. The shoulder 70S can be a circumferential face dimensioned toabut against a first circumferential face 64FA of the second component64. The retention slot 70R can be an annular groove extending along afirst (e.g., inner) diameter 70D of the first component 62. The shoulder70S and the retention slot 70R can extend in a circumferential directionT about the engine longitudinal axis A and/or assembly axis AA.

The shoulder 70S can extend radially inward from the first diameter 70Dof the first component 62 such that the retention slot 70R and shoulder70S are radially offset in a radial direction R relative to the assemblyaxis AA. The retention slot 70R can be radially outward of the shoulder70S. The retention slot 70R can extend radially outward from the firstdiameter 70D of the first component 62 relative to the assembly axis AA.

The retention ring 66 is dimensioned to be at least partially receivedin the retention slot 70R in the cold assembly state. A portion of theretention ring 66 can be dimensioned to extend outwardly of theretention slot 70R to engage another gas turbine component, such as thesecond component 64. The retention ring 66 can be dimensioned to abut asecond circumferential face 64FB of the second component 64 in theinstalled position to trap or otherwise secure the second component 64between the shoulder 70S and the retention ring 66. The first and secondcircumferential faces 64FA, 64FB can be established along opposite sidesof the second component 64. The second component 64 can include an inner(e.g., first) diameter 64ID and outer (e.g., second) diameter 640D. Thefirst and second circumferential faces 64FA, 64FB can be dimensioned toextend in the radial direction R between the inner and outer diameters64ID, 640D of the second component 64 (also shown in dashed lines inFIG. 4 ). The inner diameter 64ID of the second component 64 can bedimensioned to engage the third component 68 to establish a sealingrelationship.

The retention ring 66 can include a main body 72 dimensioned to engageand secure a gas turbine engine component, such as the second component64. The main body 72 can have various geometries, such as asubstantially circular or elliptical geometry. The main body 72 canextend in the circumferential direction T about a ring axis RA. The ringaxis RA can be substantially collinear or otherwise parallel to theassembly axis AA. The main body 72 can extend in the circumferentialdirection T about the ring axis RA to establish a continuous hoop havinga first diameter 73 and a second diameter 74, as illustrated in FIG. 4 .The first diameter 73 and second diameter 74 can be established onopposite sides of the main body 72. The first diameter 73 can be aninner diameter 66ID of the continuous hoop, and the second diameter 74can be an outer diameter 660D of the continuous hoop, as illustrated byFIG. 4 , although an opposite arrangement can be utilized in accordancewith the teachings disclosed herein. The retention ring 66 can be aunitary component. The main body 72 can extend circumferentially aboutthe engine longitudinal axis A of the engine 10, 20 to establish thecontinuous hoop. For the purposes of this disclosure, the term“continuous hoop” means a ring structure lacking any circumferentialends. The continuous hoop can be utilized to improve stiffness of theretention ring 66 and reduce liberation of the retention ring 66 thatmay otherwise be caused by vibration, cracking, droop, deformation orother movement and changes to the retention ring 66 during engineoperation. In other examples, the retention ring 66 can include one ormore separate and distinct components permanently attached or otherwisefixedly secured to each other, as illustrated by sections 66S (shown indashed lines in FIG. 4 for illustrative purposes).

The main body 72 includes a first circumferential face 75 and a secondcircumferential face 76 that extend in the circumferential direction Talong opposite sides of the main body 72. Each of the first and secondcircumferential faces 75, 76 extend in the radial direction R betweenthe first and second diameters 73, 74. The axial, circumferential andradial directions X, T, R can be established relative to the ring axisRA, assembly axis AA and/or engine axis A. The first circumferentialface 75 is dimensioned to abut a gas turbine engine component in thecold assembly state, such as the second component 64. The secondcomponent 64 can be dimensioned to extend radially inward of the firstand/or second circumferential faces 75, 76 and first and/or seconddiameters 73, 74 of the main body 70 in the assembly state, asillustrated by the inner diameter 641D of the second component 64 inFIGS. 3 and 4 .

Various materials may be utilized to construct the components 62, 64 andretention ring 66. Each component 62, 64 and retention ring 66 can beformed of a material having a high temperature capability, includingmetallic and/or non-metallic materials. Example metallic materialsinclude metals and alloys, such as nickel-based superalloys, titaniumand steel. Example non-metallic materials include ceramic-basedmaterials such as monolithic ceramics and ceramic matrix composites(CMC). Monolithic ceramics can include silicon carbide (SiC) and siliconnitride (Si₃N₄) materials. The main body 72 of the retention ring 66 cancomprise a metallic and/or non-metallic material, including any of thematerials disclosed herein.

The retention ring 66 can include one or more removal features 78 thatmay be utilized to remove the retention ring 66 from the first component62 when in the assembled position, including when the retention ring 66is captured in the retention slot 70R in the cold assembly state of theassembly 60. The main body 70 of the retention ring 66 can include atleast one or more of the removal features 78. The retention ring 66 caninclude two or more removal features 78 circumferentially distributedabout the ring axis RA, such as a total of three removal features 78, asillustrated in FIG. 4 , although fewer or more than three removalfeatures 78 can be utilized. The removal features 78 can becircumferentially distributed along the first and/or circumferentialfaces 75, 76 of the retention ring 66.

Each removal feature 78 can be dimensioned to sever for removal of theretention ring 66 and second component 64 in the cold assembly state.Each removal feature 78 can be dimensioned to sever in response toengagement with an instrument such as a cutting tool TT, as illustratedby the severed removal feature 78′ of FIG. 6 . The cutting tool TT canbe a milling tool or a saw blade. Other arrangements can be utilized toestablish the removal feature 78. In implementations, the removalfeature 78 is a frangible connection that can be snapped or otherwisesevered with a tool (e.g., plyers). The removal features 78 can beformed with the main body 72 of the retention ring 66 or may be formedin the retention ring 66 by a subsequent machining operation.

Each removal feature 78 can include a notch 79 and a first groove (e.g.,trench) 80 joined with the notch 79. The notch 79 can extend in theaxial direction X along a face 74F of the second diameter 74 between thefirst and second circumferential faces 75, 76, as illustrated in FIGS. 4and 5 . The notch 79 can extend inwardly from the face 74F of the seconddiameter 74 received in the retention slot 70R. The first groove 80 canextend in the radial direction R from a floor 79F of the notch 79 alongthe first circumferential face 75 to a face 73F of the first diameter73, as illustrated in FIG. 5 , although the opposite arrangement can beutilized such that the notch 79 extends along the face 73F of the firstdiameter 73.

In the example of FIG. 7 , the removal feature 178 includes a notch 179that joins a first groove 180 and a second groove 181 extending alongopposite sides of the main body 172. The notch 179 and first and secondgrooves 180, 181 can incorporate any of the dimensions of the notch 79and groove 80 of FIGS. 3-5 . Each of the first and second grooves 180,181 extend from the notch 179 such that the notch 179 interconnects thefirst and second grooves 180, 181. The first groove 180 can bedimensioned to extend along the first circumferential face 175. Thesecond groove 181 can be dimensioned to extend along the secondcircumferential face 176. The first and second grooves 180, 181 canextend in the radial direction R from the floor 179F of the notch 179along the respective first and second circumferential faces 180, 181 tothe face of the second diameter of the retention ring 166 (e.g., face74F of diameter 74 of FIG. 4 ). The first groove 180 can becircumferentially aligned with the second groove 181 relative to thecircumferential direction T. Incorporating the first and second grooves180, 181 can provide a mistake-proofing feature that facilitiesinstallation of the retention ring 66.

Referring back to FIGS. 3-5 , the removal feature 78 can have variousgeometries to facilitate severing the retention ring 66. The notch 79can be a scallop along the first or second diameters 73, 74 of the mainbody 70. Opposed sidewalls of the notch 79 can be dimensioned to slopeinwardly from the face 74F of the second diameter 74 to the floor 79F ofthe notch 79. The sloping surfaces can be established by fillets orbevels, for example.

The removal feature 78 can have various dimensions to facilitatesevering the retention ring 66. Referring to FIG. 5 , with continuingreference to FIGS. 3-4 , the first groove 80 can establish a first widthW1 at the floor 79F of the notch 79. The notch 79 can establish a secondwidth W2 along the one of the first and second faces 73F, 74F, such asalong the face 74F of the second diameter 74. The second width W2 can bea maximum width of the notch 79, which can be established along one ofthe first and second faces 73F, 74F, such as along the second face 74Fof the second diameter 74. The first and second widths W1, W2 can bedefined relative to the circumferential direction T. The removal feature78 can be dimensioned such that the first width W1 is less than thesecond width W2 of the notch 79. The removal feature 78 can bedimensioned such that the ratio W1:W2 is less than about 1:2, or morenarrowly between about 1:3 and about 1:5.

The first groove 80 can establish a first length L1 between the floor79F of the notch 79 and the face 73F of the first diameter 73. The notch79 can establish a first height H1. The first height H1 can be a maximumheight of the notch 79 between the floor 79F of the notch 79 and theface 74F of the second diameter 74. The first length L1 and first heightH1 can be defined relative to the radial direction R and can be definedat a common circumferential position along the first groove 80. Theremoval feature 78 can be dimensioned such that the first length L1 isgreater than the first height H1 of the notch 79. The removal feature 78can be dimensioned such that the ratio L1:H1 is greater than about 2:1,or more narrowly between about 3:1 and about 5:1. The maximum height ofthe notch 79 can be greater than or equal to about 5 percent of a heightH3 of the main body 70 of the retention ring 66 at a commoncircumferential position between the first and second diameters 73, 74relative to the radial direction R, or more narrowly less than or equalto about 50 percent of the height H3 of the main body 70. The maximumheight of the notch 79 can be greater than a maximum height H2 of theretention slot 70R (FIG. 9 ) at a common circumferential positionrelative to the assembly axis AA and/or engine axis A (FIGS. 1 and 2 ).The removal feature 78 can be dimensioned such that the ratio H1:H2 isgreater than about 0.5:1, or more narrowly greater than about 0.8:1.

The removal features 78 can be dimensioned relative to the firstcomponent 62 to facilitate removal of the retention ring 66 from theslot 70R. Each of the removal features 78 can be dimensioned such thatthe floor 79F of the notch 79 is radially offset from the retention slot70R relative to the engine and/or assembly axis A, AA to establish arespective clearance gap CG, as illustrated in FIGS. 3-4 and 6 . Anarray of the clearance gaps CG can be established circumferentiallyabout the assembly axis AA. Each clearance gap CG can be localized suchthat the clearance gaps CG are spaced apart from each other relative tothe circumferential direction T. The notches 79 can be dimensioned suchthat each clearance gap CG extends no more than 10 degrees about theassembly axis AA, or more narrowly no more than 5 degrees about theassembly axis AA, which can improve rigidity of the retention ring 66.

Each clearance gap CG can be dimensioned to receive a cutting tool TT,as illustrated in FIG. 6 . The cutting tool TT can be movable along acutting path CP (shown in dashed lines for illustrative purposes). Thecutting path CP can be established along a length of the first groove 80and can intersect the notch 79. The cutting tool TT can be movable alongthe first groove 80 to sever the retention ring 66, as illustrated bythe retention ring 66′ of FIG. 6 . The retention ring 66′ can be severedinto two or more portions, as illustrated by portions 66-1′, 66-2′. Eachof the portions 66-1′, 66-2′ of the severed retention ring 66′ can beremoved from the retention slot 70R when in the cold assembly state. Adepth of the groove 80 can be dimensioned to facilitate movement of thecutting tool TT along the cutting path CP while spacing apart thecutting tool TT from the second component 64, which can reduce alikelihood of degradation of the second component 64 during the severingoperation.

FIG. 8 illustrates an exemplary method of assembly for a gas turbineengine in a flow chart 90. The method 90 can be utilized to assemble,retain and disassemble various components of a gas turbine engine,including any of the components disclosed. Reference is made to theassembly 60 for illustrative purposes.

Referring to FIG. 9 , with continuing reference to FIG. 8 , one or morecomponents of the assembly 60 are prepared for assembly or installationat step 90A, such as the first component 62 and/or retention ring 66.Preparing the components can include causing a temporary ornon-permanent change to one or more dimensions of the respectivecomponent(s).

Step 90A can include changing a temperature of at least one of thecomponents of the assembly 60, such as the retention ring 66 and/orfirst component (e.g., support) 62 to meet a respective predeterminedtemperature threshold when the retention ring 66 is in a first (e.g.,disassembly) position at step 90A-1. Step 90A-1 can include changing thetemperature of only one, or more than one, of the components of theassembly 60, such as the first component 62 and/or retention ring 66.Step 90A-1 can include changing the temperature of the respectivecomponent(s) when the retention ring 66 is in the first position toestablish an assembly clearance AC when the retention ring 66 is in asecond (e.g., assembly) position relative to the first component 62, asillustrated by the retention ring 66″ (shown in dashed lines forillustrative purposes). The assembly clearance AC can be established bythe first diameter 73″ or the second diameter 74″ of the retention ring66″. In the illustrated example of FIG. 9 , the assembly clearance AC isestablished between the second diameter 74″ of the retention ring 66″and the diameter 70D of the first component 62 establishing theretention slot 70R.

Various techniques can be utilized to change the temperature of eachrespective component at step 90A-1. Step 90A-1 can include heating oneor more components of the assembly 60 at step 90A-2 and/or cooling oneor more of the components of the assembly 60 at step 90A-3. The heatingat step 90A-1 can establish an expanded state of the respectivecomponent, such as one of the first component 62 and/or retention ring66. The cooling at step 90A-1 can establish a contracted state of therespective component, such as another one of the first component 62and/or retention ring 66.

Various techniques can be utilized to heat and/or cool the respectivecomponents of the assembly 60. Step 90A-2 can include positioning thefirst component 62 in a first environment ENV1 (shown in dashed linesfor illustrative purposes) and then heating the first component 62 abovea first predetermined temperature threshold to cause the retention slot70R of the first component 62 to expand relative to the assembly axisAA. Various techniques can be utilized to perform the heating, such aswrapping the first component 62 in a heat blanket having heating coils.Step 90A-3 can include positioning the retention ring 66 in a secondenvironment ENV2 (shown in dashed lines for illustrative purposes) andthen cooling the retention ring 66 below a second predeterminedthreshold to cause the first diameter 73 and/or second diameter 74 ofthe retention ring 66 to contract relative to the assembly axis AA.Various techniques can be utilized to perform the cooling, such aspositioning the retention ring 66 in a dry ice or nitrogen environment.The second predetermined threshold associated with the cooling in step90A-3 can be less than the first predetermined threshold associated withthe heating in step 90A-2. The first and/or second predeterminedthresholds can be defined to establish the assembly clearance AC. Thepredetermined thresholds can be defined according to one or moredimensions, materials, stacking tolerances, etc., of the components ofthe assembly 60 in the cold assembly state. Each predeterminedtemperature threshold can be defined such that the predeterminedtemperature threshold is not met during operation of the engine 10, 20in a hot assembly state.

At step 90B, one or more of the components prepared at step 90A aremoved to respective assembly positions. Step 90B can include moving thesecond component 64 along the assembly axis AA such that the face 64FAsecond component 64 abuts against, or is otherwise adjacent to, theshoulder 70S of the first component 62. Step 90B can include moving theretention ring 66 along the assembly axis AA from the first position tothe second position to establish the assembly clearance AC. Step 90B canoccur such that the retention ring 66 is axially aligned with, but isspaced apart from, the retention slot 90R relative to the assembly axisAA, as illustrated by the retention ring 66″ of FIG. 9 . The retentionslot 70R can be established along the first diameter 70D of the firstcomponent 62. The assembly clearance AC can be established between theouter diameter 660D of the retention ring 66 and the first diameter 70Dof the first component 62. The first diameter 70D can be a radiallyinward facing surface of the first component 62 relative to the assemblyaxis AA.

Referring to FIG. 3 , with continuing reference to FIGS. 8 and 9 , atstep 90C one or more of the components of the assembly 60 are secured toestablish the cold assembly state. Step 90C can include securing thesecond component 64 and retention ring 66 relative to the firstcomponent 62. Step 90C can include securing the second component 64 withthe retention ring 66.

Step 90C can include reducing the assembly clearance AC to establish thecold assembly state at step 90C-1. Step 90C-1 can include reducing theassembly clearance AC in response to the temperature of the component(s)prepared at step 90A no longer meeting the respective predeterminedtemperature threshold(s). Reducing the temperature can include applyingan opposite or offsetting amount of heating or cooling to the respectivecomponent, or allowing the respective component to rest or normalizesuch that the component approaches the cold assembly state. Reducing thetemperature can occur at a position outside of the respectiveenvironment ENV1/ENV2.

Reducing the assembly clearance AC can occur such that the seconddiameter 74 of the retention ring 66 is captured in the retention slot70R. Step 90C-1 can occur such that the retention ring 66 expands orotherwise moves in a first direction D1 (FIG. 9 ) and into the retentionslot 70R. Step 90C-1 can occur such that the first component 62contracts or otherwise moves in a second direction D2 (FIG. 9 ) suchthat the retention ring 66 is captured in the retention slot 70R. Thefirst direction D1 can be a radially outward direction relative to theassembly axis AA and the second direction D2 can be a radially inwarddirection relative to the radial direction R and/or assembly axis AA, orvice versa. The first and/or second directions D1, D2 can besubstantially perpendicular or otherwise transverse to the assembly axisAA. The retention ring 66 can be dimensioned to establish aninterference fit with walls of the retention slot 70R in the coldassembly state.

Reducing the assembly clearance AC can occur such that the secondcomponent 64 is trapped between the shoulder 70S of the first component62 and the first circumferential face 75 of the retention ring 66.Reducing the assembly clearance AC can occur such that a respectiveclearance gap CG is established between the first component 62 and thefloor 79F of the notch 79, as illustrated in FIGS. 3-4 and 6 .

Referring to FIG. 6 , with continuing reference to FIGS. 4 and 8 , atstep 90D one or more components such as the retention ring 66 can beremoved from the assembly 60 to establish a disassembly state. Step 90Dcan including causing a permanent change to the respective component atstep 90D-1, which can occur prior to and/or during the removal. Step90D-1 can include at least partially or completely severing theretention ring 66 into one or more portions, as illustrated by theportions 66-1′, 66-2′ of the retention ring 66′. Severing the retentionring 66 can occur in response to moving the cutting tool TT into theclearance gap CG and then along the cutting path CP including along thefirst groove 80 to establish a pathway PP. In the implementation of FIG.7 , step 90D-1 can include moving the cutting tool TT along a cuttingpath CP intersecting both the first and second grooves 180, 181 toestablish a pathway PP between the first and second grooves 180, 181(shown in dashed lines for illustrative purposes).

Step 90D can include removing at least one portion (e.g., 66-1′, 66-2′)of the severed retention ring 66′ from the retention slot 70R, and thenremoving the second component 64 from the first component 62, which canoccur when the third component 68 is in an assembled position (FIG. 3 ).The cutting path CP can be substantially perpendicular or otherwisetransverse to the assembly axis AA. In examples, step 90D-1 includesmoving the cutting tool TT in a radially inward direction relative tothe assembly axis AA.

The retention rings disclosed herein can be utilized to facilitateremoval of component(s) retained in the assembly, while reducing alikelihood of degradation of the retained component(s). The disclosedretention rings can be dimensioned to establish a relative greaterstiffness with a lower likelihood of liberation during engine operation.

It should be understood that relative positional terms such as“forward,” “aft,” “upper,” “lower,” “above,” “below,” and the like arewith reference to the normal operational attitude of the vehicle andshould not be considered otherwise limiting.

Although the different examples have the specific components shown inthe illustrations, embodiments of this disclosure are not limited tothose particular combinations. It is possible to use some of thecomponents or features from one of the examples in combination withfeatures or components from another one of the examples.

Although particular step sequences are shown, described, and claimed, itshould be understood that steps may be performed in any order, separatedor combined unless otherwise indicated and will still benefit from thepresent disclosure.

The foregoing description is exemplary rather than defined by thelimitations within. Various non-limiting embodiments are disclosedherein, however, one of ordinary skill in the art would recognize thatvarious modifications and variations in light of the above teachingswill fall within the scope of the appended claims. It is therefore to beunderstood that within the scope of the appended claims, the disclosuremay be practiced other than as specifically described. For that reasonthe appended claims should be studied to determine true scope andcontent.

1. An assembly for a gas turbine engine comprising: a support extendingabout an assembly axis and including a retention slot; and a retentionring received in the retention slot, the retention ring comprising: amain body extending in a circumferential direction about the assemblyaxis to establish a continuous hoop having a first diameter and a seconddiameter, the main body including first and second circumferential facesalong opposite sides of the main body that extend in a radial directionbetween the first and second diameters, and the first circumferentialface is dimensioned to abut a gas turbine engine component; wherein themain body includes at least one removal feature, the at least oneremoval feature includes a notch and a first groove, the notch extendsin an axial direction along a face of the second diameter between thefirst and second circumferential faces, and the first groove extends inthe radial direction from a floor of the notch along the firstcircumferential face to a face of the first diameter; wherein the floorof the notch is radially offset from the retention slot relative to thelongitudinal axis to establish a clearance gap, and the clearance gap isdimensioned to receive a cutting tool moveable along the first groove tosever the retention ring.
 2. The assembly as recited in claim 1, whereinthe at least one removal feature includes a plurality of removalfeatures distributed about the assembly axis.
 3. The assembly as recitedin claim 1, wherein the first diameter is an inner diameter of thecontinuous hoop, and the second diameter is an outer diameter of thecontinuous hoop.
 4. The assembly as recited in claim 1, wherein the atleast one removal feature includes a second groove extending in theradial direction from the floor of the notch along the secondcircumferential face to the face of the second diameter.
 5. The assemblyas recited in claim 4, wherein the first groove is aligned with thesecond groove relative to the circumferential direction.
 6. The assemblyas recited in claim 1, wherein: a first width of the first groove at thefloor of the notch is less than a maximum width of the notch, the firstwidth and the maximum width relative to the circumferential direction;and a first length of the first groove is greater than a maximum heightof the notch, the first length and the maximum height relative to theradial direction.
 7. The assembly as recited in claim 1, wherein themain body comprises a metallic material.
 8. A gas turbine enginecomprising: a support extending about an engine longitudinal axis, thesupport including a shoulder and a retention slot; a gas turbine enginecomponent; a retention ring received in the retention slot, wherein theretention ring includes a main body having a first diameter and a seconddiameter, the main body includes first and second circumferential facesalong opposite sides of the main body, and the first circumferentialface is dimensioned to abut the gas turbine engine component; whereinthe main body includes at least one removal feature, the at least oneremoval feature includes a notch and a first groove, the notch extendsinwardly from a face of the second diameter that is received in theretention slot, and the first groove extends radially from a floor ofthe notch along the first circumferential face; and wherein the floor ofthe notch is radially offset from the retention slot relative to theengine longitudinal axis to establish a clearance gap, and the clearancegap is dimensioned to receive a cutting tool movable along the firstgroove to sever the retention ring.
 9. The gas turbine engine as recitedin claim 8, wherein the main body extends circumferentially about theengine longitudinal axis to establish a continuous hoop.
 10. The gasturbine engine as recited in claim 8, wherein the first diameter is aninner diameter of the retention ring, the second diameter is an outerdiameter of the retention ring, and the groove extends from the notch tothe inner diameter of the retention ring.
 11. The gas turbine engine asrecited in claim 10, wherein the shoulder and the retention slot extendcircumferentially about the engine longitudinal axis, the retention slotis radially outward of the shoulder, and the gas turbine enginecomponent extends radially inward of the first circumferential face ofthe main body.
 12. The gas turbine engine as recited in claim 8, whereinthe at least one removal feature includes a plurality of removalfeatures circumferentially distributed about an axis of the retentionring.
 13. The gas turbine engine as recited in claim 8, wherein the gasturbine engine component is an annular seal dimensioned to engage arotatable component.
 14. A method of assembly for a gas turbine enginecomprising: changing a temperature of at least one of a retention ringand a support to meet a respective predetermined temperature thresholdwhen the retention ring is in a first position to establish an assemblyclearance when the retention ring is in a second position relative tothe support, the assembly clearance established between a seconddiameter of the retention ring and a retention slot of the support;wherein the retention ring includes a main body establishing acontinuous hoop including a first diameter and the second diameter, themain body includes at least one removal feature having a notch and afirst groove, the notch extends along the second diameter of theretention ring, and the first groove extends along a firstcircumferential face of the main body to the first diameter of theretention ring; moving a gas turbine engine component along an assemblyaxis such that the gas turbine engine component is adjacent to ashoulder of the support; moving the retention ring along the assemblyaxis from the first position to the second position to establish theassembly clearance such that the retention ring is axially aligned with,but is spaced apart from, the retention slot; reducing the assemblyclearance in response to the temperature no longer meeting therespective predetermined temperature threshold, wherein the reducingstep occurs such that the second diameter of the retention ring iscaptured in the retention slot, such that the gas turbine enginecomponent is trapped between the shoulder of the support and the firstcircumferential face of the retention ring, and such that a clearancegap is established between the support and a floor of the notch; andsevering the retention ring in response to moving a cutting tool intothe clearance gap and then along the first groove.
 15. The method asrecited in claim 14, wherein the at least one removal feature includes aplurality of removal features circumferentially distributed along thefirst circumferential face.
 16. The method as recited in claim 14,further comprising: removing at least one portion of the severedretention ring from the retention slot, and then removing the gasturbine engine component from the support.
 17. The method as recited inclaim 16, wherein: a maximum height of the notch is greater than amaximum height of the retention slot at a common circumferentialposition relative to an engine longitudinal axis.
 18. The method asrecited in claim 16, wherein: the at least one removal feature includesa second groove extending from the notch, the notch interconnects thefirst and second grooves, and the second groove extends along a secondcircumferential face of the retention body such that the second grooveis circumferentially aligned with the first groove; and the severingstep includes moving the cutting tool along a cutting path intersectingboth the first and second grooves to establish a pathway between thefirst and second grooves.
 19. The method as recited in claim 14, whereinthe second diameter of the retention ring is an outer diameter, theretention slot is established along a radially inward facing surface ofthe support relative to the assembly axis, the assembly clearance isestablished between the outer diameter of the retention ring and theradially inward facing surface of the support, the respectivepredetermined temperature threshold includes a first predeterminedtemperature threshold associated with the support and a secondpredetermined temperature threshold associated with the retention ring,and the step of changing the temperature comprises: heating the supportabove the first predetermined temperature threshold to cause theretention slot of the support to expand relative to the assembly axis;and cooling the retention ring below the second predetermined thresholdto cause the outer diameter of the retention ring to contract relativeto the assembly axis, the second predetermined threshold being less thanthe first predetermined threshold.
 20. The method as recited in claim14, wherein the support comprises a first metallic material, and themain body comprises a second metallic material.